Split gimbal

ABSTRACT

A gimbal having a split design, which can be used in an assembly for actuating an aerodynamic high lift device, is described. The gimbal enables a rotating load path when a force is transferred from the actuator to the high lift device via the gimbal. In particular, the split design can include two receivers which can be coupled to posts extending from a nut. The nut can be secured to a shaft which receives a force generated by the actuator. In one embodiment, the actuator can rotate the shaft to cause the gimbal to translate along the shaft. The split design provides a more compact form factor and is lighter in weight than traditional gimbal designs.

TECHNICAL FIELD

This disclosure generally relates to actuating high lift devices onairplanes. More specifically, this disclosure relates to a gimbal whichprovides extra degrees of freedom of motion when an actuator is used toactuate a high lift device.

BACKGROUND

Modern aircraft, such as large passenger jets, need to operate atvarious speeds, including a lower speed during take-off and landing andhigher speed during cruise. To accommodate operations at the variousspeeds, the aircraft wings include high lift devices. Typically, thehigh lift devices are actuatable relative to a fixed portion of thewing. By changing positions of the high lift devices relative to thefixed portion of the wing, various aerodynamic effects are achieved. Theaerodynamics effects are used to control the aircraft. For example, theaerodynamic effects are used to generate lift during low speedoperations, such as take-off and landing.

Actuators are used to change the position of the high lift device. Forexample, an actuator installed in a wing can be used to change aposition of a flap on the wing. The actuators generate a motion, whichis transferred, via an assembly, from the actuator to the high liftdevice. For aerodynamic, weight, cost and integration reasons, it isdesirable for the assembly, which transfers the motion from the actuatorto the high-lift device, to be as light-weight and compact as possible.

SUMMARY

Assemblies for actuating an aerodynamic high lift device on an aircraftare described. In one embodiment, a force generated by an actuator canbe transferred to the aerodynamic high lift device via a gimbal. Thegimbal can utilize a split design, which provides a compact form factor.

The gimbal can be generally characterized as including 1) a nut having afirst post, a second post and a first aperture where the aperture isconfigured to receive a shaft; 2) a first receiver, 3) a second receiverand 4) one or more fasteners for securing the first receiver to thesecond receiver. The first receiver, the second receiver and the nut canbe assembled such that the nut is secured in place relative to the firstreceiver and the second receiver via the first post and the second post.Further, the nut can be disposed within a second aperture formed by thefirst receiver and the second receiver.

The first receiver can include a first top portion, which partiallysurrounds the first post, ii) a first bottom portion, which partiallysurrounds the second post and iii) a first rotational attachment point.The second receiver can include i) a second top portion, which partiallysurround the first post, ii) a second bottom portion, which partiallysurround the second post and iii) a second rotational attachment point.The gimbal can be configured to receive a force via the shaft whichcauses the gimbal to translate wherein a translational movement of thegimbal causes a driver arm coupled to the first rotational attachmentpoint and the second rotational attachment point to rotate about arotational axis.

In particular embodiments, the nut can be threaded and can be configuredto receive a threaded shaft. The threaded shaft can be configured torotate which causes the gimbal to translate along the threaded shaft. Inanother embodiment, the nut can be secured at a fixed location to theshaft. A translational motion of the shaft can cause the gimbal totranslate.

In other embodiments, the first receiver and the second receiver canhave a common shape. Yet further, the second aperture can be circular.The diameter of the second aperture can smaller than a height of the nutbetween the first post and the second post.

In yet other embodiments, a first bushing can cover the first post and asecond bushing can cover the second post. The first top portion and thesecond top portion of the first receiver and the second receiver cansurround the first bushing and the first post. The first bottom portionand the second bottom portion can surround the second bushing and thesecond post. A first fastener coupled to the first receiver and thesecond receiver can be configured to secure the first bushing in placeand a second fastener coupled to the first receiver and the secondreceiver can be configured to secure the second bushing in place.

In other embodiments, the driver arm can be coupled to an aerodynamichigh lift device. The driver arm can be coupled to the gimbal via thefirst rotational attachment point and the second attachment point toprevent the shaft from being bent when the gimbal translates. Theaerodynamic control surface can be located on a wing, a horizontalstabilizer or a vertical stabilizer.

Another aspect of the disclosure can be related to an assembly foractuating an aerodynamic high lift device on an aircraft. The assemblycan comprise 1) an actuator coupled to a shaft where the shaft isconfigured to receive a force from the actuator; 2) a gimbal coupled tothe shaft, 3) a driver arm coupled to the gimbal and 4) an aerodynamichigh lift device coupled to the driver arm. A force from the actuatorcan cause the gimbal to translate, which can cause the first end of thedriver arm to translate and rotate about a rotational axis. The rotationand translation of the first end can transfer a second force to thesecond end of the driver arm where the second force can cause theaerodynamic high lift device to actuate.

The gimbal can include 1) a nut having a first post, a second post and afirst aperture wherein the aperture is configured to receive the shaft;2) a first receiver including i) a first top portion, which canpartially surround the first post, ii) a first bottom portion, which canpartially surround the second post and iii) a first rotationalattachment point; 3) a second receiver including i) a second topportion, which can partially surround the first post, ii) a secondbottom portion, which can partially surround the second post and iii) asecond rotational attachment point; 4) at least one fastener which cansecure the first receiver to the second receiver to form a secondaperture where the nut is disposed within the second aperture. Thedriver arm can be rotationally coupled to the first rotationalattachment point and the second rotational point on a first end and theaerodynamic high lift device on a second end.

In particular embodiments, the assembly can be located in one of a wingof an aircraft, a horizontal stabilizer of the aircraft or a verticalstabilizer of the aircraft. In addition, the driver arm can be coupledto the gimbal via the first rotational attachment point and the secondattachment point to prevent the shaft from being bent when the gimbaltranslates. In addition, the nut can be threaded and can be configuredto receive a threaded shaft. The shaft can be configured to rotate whichcauses the gimbal to translate along the shaft. Yet further, an end capcan be attached at the end of the shaft which is configured to keep thenut from rotating off of the shaft. In yet other embodiments, the nutcan be secured at a fixed location to the shaft where a translationalmotion of the shaft causes the gimbal to translate.

In further embodiments, the first receiver and the second receiver canhave a common shape. In addition, the second aperture can be circularwhere a diameter of the second aperture can smaller than a height of thenut between the first post and the second post. In a particularembodiment, a first bushing can cover the first post and a secondbushing can cover the second post where the first top portion and thesecond top portion surround the first bushing and the first post andwhere the first bottom portion and the second bottom portion surroundthe second bushing and the second post.

Another aspect of the disclosure can be related to a method of assembly.The method can be generally characterized as including 1) attaching ashaft to an actuator; 2) attaching a nut including a first post and asecond post to the shaft; 3) attaching a first receiver and a secondreceiver to the first post and the second post of the nut where thefirst receiver and the second receiver can surround the nut and can fixan orientation of the nut relative to the first receiver and the secondreceiver and where the first receiver can includes a first rotationalattachment point and where the second receiver can include a secondrotational attachment point; 4) fastening the first receiver to thesecond receiver; 5) attaching a driver arm on a first end to the firstrotational attachment point and the second rotational attachment pointwhere the driver arm is rotationally coupled to the first rotationalattachment point and the second rotational attachment point; and 6)attaching an aerodynamic high lift device to a second end of the driverarm.

In particular embodiments, the actuator can be configured to apply aforce to the shaft which can causes the nut, the first receiver and thesecond receiver to translate. The translational motion of the nut cancause the first end of the driver arm to translate and to rotate about arotational axis through the first rotational attachment point and thesecond rotational attachment point. This motion can transfer a secondforce to the second end of the driver arm, which can cause theaerodynamic high lift device to actuate.

In addition, the force can be rotational force which causes the shaft torotate. The rotation of the shaft can cause the nut, the first receiverand the second receiver to translate along the shaft. The nut and theshaft can be threaded.

BRIEF DESCRIPTION OF THE DRAWINGS

Having thus described examples of the disclosure in general terms,reference will now be made to the accompanying drawings, which are notnecessarily drawn to scale, and wherein like reference charactersdesignate the same or similar parts throughout the several views, andwherein:

FIG. 1 is a perspective view illustrating an airplane and aerodynamichigh lift devices, according to one aspect of the present disclosure.

FIG. 2 is a perspective view of an assembly including an actuator and agimbal used to provide a load path from the actuator to a high liftdevice according to one aspect of the present disclosure

FIG. 3 is an expanded perspective view of the gimbal shown in FIG. 2,according to one aspect of the present disclosure.

FIGS. 4 and 5 are perspective views of the gimbal shown in FIG. 2,according to aspects of the present disclosure.

FIGS. 6A and 6B are block diagrams of an assembly including an actuator,a gimbal and a driver arm coupled to the gimbal, according to one aspectof the present disclosure.

FIG. 7 is block diagram of a method of assembling a gimbal, according toone aspect of the present disclosure.

FIG. 8 is a block diagram of an aircraft production and servicemethodology that may utilize the gimbal described with respect to FIGS.2-7, according to one aspect of the present disclosure

FIG. 9 is a schematic illustration of an aircraft that may utilize agimbal in accordance with FIGS. 2-7, according to one aspect of thepresent disclosure.

DETAILED DESCRIPTION

In the following description, numerous specific details are set forth inorder to provide a thorough understanding of the presented concepts. Thepresented concepts may be practiced without some or all of thesespecific details. In other instances, well known process operations havenot been described in detail so as to not unnecessarily obscure thedescribed concepts. While some concepts will be described in conjunctionwith the specific examples, it will be understood that these examplesare not intended to be limiting.

Reference herein to “one example” or “one aspect” means that one or morefeature, structure, or characteristic described in connection with theexample or aspect is included in at least one implementation. The phrase“one example” or “one aspect” in various places in the specification mayor may not be referring to the same example or aspect.

Introduction

Assemblies for actuating an aerodynamic high lift device on an aircraftare described. In one embodiment, a shaft extending from the actuatorcan be used to impart a force generated by the actuator via a pluralityof mechanical linkages to the aerodynamic high lift device. A gimbal canbe coupled to the shaft to provide a rotational interface between adriver arm coupled to the aerodynamic high lift device and the shaft.The gimbal and its associated rotational interface can minimize thelikelihood of the shaft being bent during operation.

A split design for the gimbal is described. The split design can includetwo receivers which can be coupled to posts on a nut. The nut can besecured to the shaft, which is coupled to the actuator, and the driverarm can be coupled to rotational attachment points on the receivers. Thesplit design can provide more compact form factor and is lighter inweight than traditional gimbal designs. Although the split design isdescribed with respect to actuating a high lift device on an aircraft,it can be used in other applications. Thus, this implementation isdescribed for the purposes of illustration only and is not meant to belimiting.

In more detail, an airplane and aerodynamic high lift devices used on anaircraft are described with respect to FIG. 1. With respect to FIG. 2,an assembly 40 including an actuator and a gimbal is described. Thegimbal can be part of a force transfer assembly used to provide a loadpath from the actuator to a high lift device or another moveablestructure on the aircraft.

With respect to FIGS. 3, 4 and 5, the gimbal shown in FIG. 2 isdiscussed. The gimbal includes a nut for receiving a shaft from theactuator. A first receiver and a second receiver secure the nut in placeand provide a rotational interface. With respect to FIGS. 6A and 6B, anassembly including an actuator, a gimbal and a driver arm coupled to thegimbal is described. The driver arm can be attached directly to anaerodynamic high lift device, such as a flap (or indirectly attached viaone or more additional linkages).

With respect to FIG. 7, a method of installing a gimbal is described.With respect to FIG. 8, an aircraft production and service methodologythat may utilize the gimbal described with respect to FIGS. 2-7 isdiscussed. Finally, with respect to FIG. 9, a schematic illustration ofan aircraft that may utilize the gimbal in accordance with FIGS. 2-7 isdiscussed.

Aerodynamic High Lift Devices on an Aircraft

FIG. 1 is a perspective view illustrating an airplane 2 and itsassociated aerodynamic high lift devices. On the wings 25, slats 5 areused near the leading edge of each wing. Near the trailing edge,spoilers 4, inboard (IB) flap 6, flaperon 8 and outboard (OB) flap 10,and an aileron 12 are provided on each wing. The aerodynamic high liftdevices, such as the inboard flap 6, can be configured to articulate insome manner, relative to the wings 25.

This flap configuration is provided for the purposes of illustrationonly and is not meant to be limiting. For example, on a Boeing 737,there is no flaperon. As another example, some 777x designs includethree flaps per wing whereas this design includes two flaps per wings.

The empennage 27 is provided with aerodynamic high lift devicesincluding a vertical stabilizer 13, rudder 16 and rudder tab 18. Thehorizontal stabilizer 14 is provided with an elevator 20, which is anaerodynamic high lift device. The rudder 16 and rudder tab 18 can beconfigured to move relative to the vertical stabilizer and the elevatorcan be configured to move relative to the horizontal stabilizer.

The aerodynamic high lift devices, described above, utilize actuators toimpart forces which cause the high lift devices to change positions. Forexample, actuators can be used to change the flap configurations duringtake-off and landing. A force transfer assembly can be used to transferforces generated by the actuator to an aerodynamic high lift device orsome other moveable structure on the aircraft. With respect to FIGS.2-7, a split gimbal design is described which can be used as part of aforce coupling mechanism between an actuator and an aerodynamic highlift devices.

Split Gimbal and Force Coupling Mechanisms

FIG. 2 is a perspective view of an assembly 40 including an actuator 50,a gimbal 60 and shaft 58. In one embodiment, the assembly can be mountedin a wing of an aircraft, such as wing 25 shown in FIG. 1. In otherembodiments, the assembly 40 can be mounted in a vertical stabilizer orhorizontal stabilizer of an aircraft (e.g., see vertical stabilizer 13and horizontal stabilizer 14 in FIG. 1).

The gimbal 60 and the shaft can be used to transfer a motion generatedby the actuator 50 to an aerodynamic high lift device. In oneembodiment, a first end of a driver arm can be coupled to the gimbal 60and a second end of the driver arm can be coupled directly or via one ormore linkages to the aerodynamic high lift device (e.g., see FIGS. 6Aand 6B). In this example, the actuator 50 can be configured to generatea motion as a rotational output which is transferred to the shaft 58. Ingeneral, the gimbal can be used to transfer a motion between anactuator, such as 50, and any type of moveable structure on an aircraft.Thus, the use of aerodynamic high lift device is provided for thepurposes of illustration only and is not meant to be limiting.

In one embodiment, the shaft 58 can be a threaded shaft. The gimbal 60can include a nut 62 which is threaded. The nut 62 can be configured toreceive the shaft. For example, the nut can be rotated onto the shaft.The rotation of the shaft 58 can cause a translational movement 63 ofthe shaft 58. In particular, when the shaft 58 is rotated in a firstdirection the gimbal 60 can translate along the shaft 58 in a seconddirection and when the shaft is rotated in a third direction, oppositethe first direction, the gimbal 60 can translate along the shaft 58 in afourth direction opposite the second direction.

In particular embodiments, the shaft 58 can be between two and fiveinches in diameter. Thus, the nut 62 can be sized to accommodate theshaft (e.g., between two and five inches). This diameter is provided forthe purposes of illustration only in other applications, such asnon-aircraft applications, a smaller or larger diameter shaft can beutilized. The shaft 58 can have an end cap 61. The end cap 61 canprevent the gimbal from rotating off an end of the shaft 58. In oneembodiment, the end cap 61 can be removable to allow the nut 62 to bethreaded onto the shaft 58.

The gimbal 60 can include rotational attachment points, such asrotational attachment point 56. A driver arm coupled to the gimbal 60via the rotational attachment points can rotate and translate when thegimbal 60 translates. The rotationally coupling the driver arm to thegimbal 60 can prevent the shaft 58 from being bent when the gimbaltranslates and the driver arm is actuated or at least reduce thelikelihood of the shaft being bent.

In an alternate embodiment, the actuator can be a piston type actuator.The output of the actuator can be a linear motion which causes the shaft58 to translate back and forth. In this example, the gimbal 60 can besecured to the shaft in a fixed location. Thus, when the shafttranslates back and forth the gimbal 60 can also translate back andforth. The motion of the gimbal can transfer a force to a driver armrotationally coupled to the gimbal 60 via the rotational attachmentpoints, such as rotational attachment point 56.

FIG. 3 is an expanded perspective view of the gimbal 60 shown in FIG. 2.The gimbal 60 can include a nut 62 with a first aperture 66. Asdescribed above with respect to FIG. 2, via the first aperture 66, thenut can be configured to receive a shaft. For example, the nut 62 andthe shaft can be threaded to allow the nut to be threaded onto to theshaft.

The nut 62 can include a first post 64 a and a second post 64 b. Thefirst post 64 a and the second post 64 b are circularly shaped. Thefirst post 64 a and the second post 64 b can be aligned along an axis.The orientation of the axis relative to the shaft, as shown in FIGS. 2,6A and 6B is shown for the purposes of illustration only and is notmeant to be limiting.

In one embodiment, a first bushing 68 a can be placed over the firstpost 64 a and a second bushing 68 b can be placed over the second post64 b. The first bushing 68 a and the second bushing 68 b have an outercircular shape and an inner circular shape to fit over the first post 64a and the second post 64 b. In other embodiments, the first bushing 68 aand the second bushing 68 b can have a different outer shape, such as arectangular shape.

The nut 62 alone or nut 62, first bushing 68 a and second bushing 68 bcan be secured in place using a first receiver 70 a and second receiver70 b. The first receiver 70 a can include a first top portion with afirst opening 74 a. Via the first opening 74 a, the first top portioncan partially surround the first bushing 68 a and first post 64 a oralternatively the first post 64 a alone when a bushing is not used. Inone embodiment, a shape of the first opening 74 a can conform to anouter shape of bushing 68 a or first post 64 a.

The first receiver 70 a can include a first bottom portion with a secondopening 74 b. Via second opening 74 b, the first bottom portion canpartially surround the second bushing 68 b and second post 64 b oralternatively the second post 64 b alone when a bushing is not used. Inone embodiment, a shape of the second opening 74 b can conform to anouter shape of the second bushing 68 b or second post 64 b.

The second receiver 70 b can include a second top portion with anopening (not shown), which is opposite first opening 74 a. Via theopening, the second top portion can partially surround the first bushing68 a and first post 64 a or alternatively the first post 64 a alone whena bushing is not used. In one embodiment, a shape of the opening canconform to an outer shape of the first bushing 68 a or first post 64 a

The second receiver 70 b can include a first bottom portion with a thirdopening 74 c. Via the third opening 74 c, the first bottom portion canpartially surround the second bushing 68 b and second post 64 b oralternatively the second post 64 b alone when a bushing is not used. Inone embodiment, a shape of the third opening 74 c can conform to anouter shape of the second bushing 68 b or second post 64 b.

In one embodiment, the first receiver and the second receiver can beconfigured to be fastened together such that the first receiver 70 a andthe second receiver 70 b are brought into contact. The first receiverand the second receiver can be secured together using at least onefastener, such as but not limited to one or more bolts, one or moreclamps, an adhesive or combinations thereof. In this embodiment, thefirst bushing 68 a and the second bushing 68 b, as well as the firstpost 64 a and second post 64 b, can be completed surrounded by the firstreceiver 70 a and the second receiver 70 b.

When the first receiver 70 a and the second receiver 70 b are broughtinto contact, the openings, such as 74 a and 74 b, form a circle whichsurrounds the first bushing 68 a. The circular opening formed by opening74 a and 74 b can allow the first bushing 68 a and/or the first post 64a to rotate relative to the first receiver 70 a and the second receiver70 b. In general, the interface between the nut 62 and the receivers, 70a and 70 b, whether or not a bushing is used, can be configured to allowthe nut 62 rotate relative to the receivers.

In one embodiment, when a bushing is used, the openings, such as 74 aand 74 b, and the bushing, such as 68 a, can be shaped to allow thebushing to rotate relative to the nut or the receivers. In anotherembodiment, the openings, such as 74 a and 74 b, and the bushing, suchas 68 a, can be shaped to allow only the nut 62 to rotate relative tothe bushing. Thus, the bushing can be held in place relative to thereceivers.

In addition, when the first receiver 70 a and the second receiver 70 bare brought into contact, the inner profiles 75 of the receivers form asecond aperture, which is circularly shaped. The nut 62 is disposedwithin the second aperture and is surrounded by the first receiver 70 aand the second receiver 70 b. In alternate embodiments, the innerprofiles of the receivers can form a non-circular shape, such as anovular shape or a rectangular shape. Thus, the circular shape isprovided for the purposes of illustration only and is not meant to belimiting.

In one embodiment, the first receiver 70 a and the second receiver 70 bcan have a common shape. In alternate embodiments, the first receiver 70a and second receiver 70 b can be shaped differently from one another.The first receiver 70 a, the second receiver 70 b, the nut 62, the firstbushing 68 a and the second bushing 68 b can be generally formed from ametal, such as case hardened steel or titanium. Different metalcompositions can be used for the different parts.

The first receiver 70 a can include a first rotational attachment point72 a. The second receiver 70 b can include a second rotationalattachment point 72 b. Via the first rotational attachment point 72 aand the second rotational point 72 b, a mechanism, such as a driver arm102 (see FIGS. 6A and 6B) can be coupled to the gimbal 60. When thegimbal 60 translates, the driver arm can translate and can rotate abouta rotational axis.

In one embodiment, the rotational attachment points can be about 0.7inches across. The distance across the gimbal 60 as measured from theends of the rotational attachment points can be about 6.6 inches. Thediameter 82 can be about 4.5 inches. In alternate embodiments, thediameter 82 can range from one to ten inches across and the distance asmeasure across the rotational attachment points can be between 1.5 totwelve inches across. As mentioned above, the gimbal 60 can be formedfrom a metal such as steel or titanium.

The gimbal 60 is described with respect to an aerospace application.This example is provided for the purposes of illustration only and isnot meant to be limiting. The split gimbal design illustrated in FIG. 3can be used in other non-aerospace applications and can be sizedaccordingly.

FIGS. 4 and 5 are perspective views of the gimbal 60 shown in FIG. 2. InFIGS. 4 and 5, the first receiver 70 a and the second receiver 70 b areshown in contact with one another to fix an orientation of the nut 62relative to the first receiver 70 a and the second receiver 70 b. Asdescribed with respect to FIG. 2, the inner profile of the receivers isa circular shape. The diameter 82 of the circle is smaller than theheight of the nut between the first post and the second post. Thediameter 82 is also smaller than the height between the top of the firstbushing and the bottom of the second bushing.

In a traditional design, a single integrally formed component is used tosurround the nut 62 and provide the rotational attachment points. Thus,to accommodate the nut 62 and allow it to be installed, a largerdiameter is required as compared to the split gimbal design with thefirst receiver 70 a and the second receiver 70 b. Thus, the split gimbaldesign allows for a more compact and light weight design as compared tothe traditional design. Thus, the split gimbal design provides a methodto enhance the operational efficiency of a gimbal assembly via lighterweight, more compactness and more flexibility when assembling thegimbal.

FIG. 5 illustrates one example of a fastening scheme for securing thefirst receiver 70 a to the second receiver 70 b. Structures with twobolt openings, such as 92 a and 92 b, are formed on the first topportion of the first receiver 70 a and the second top portion of thesecond receiver 70 b. Via the bolt openings, two bolts can be insertedthrough the structures. The two bolts can be threaded to receive a nuton end. The nuts can be threaded onto to the bolt to secure the firstreceiver 70 a to the second receiver 70 b. Similar structures can befound on the first bottom portion of the first receiver 70 a and thesecond bottom portion of the second receiver 70 b and threaded bolts canbe used in a similar manner as described for the top portions of thereceivers.

Additional structures on the first top portion of first receiver 70 aand the second top portion of the second receiver 70 b can be used tosecure the first bushing 68 a in place. The structures include openings,such as an opening 94, which allow a first fastener (e.g., a bolt orpin) to be inserted. The first bushing 68 a can include a slot 90 forguiding the bolt or pin. The bolt or pin can hold the first bushing 68 ain place and also can help secure the first receiver to the secondreceiver. A similar structure can be used with a second fastener tosecure the second bushing in place on the bottom of the gimbal 60.

FIGS. 6A and 6B are block diagrams of an assembly 100 including theactuator 50, the gimbal 60 and a driver arm 102 coupled to the gimbal.The driver arm 102 on a first end is coupled to the rotational interface104. The rotational interface 104 can use the first rotationalattachment point and the second rotational attachment point on thegimbal 60 (e.g., see FIG. 5). On the second end, the driver arm 102 caninclude an aerodynamic high lift device interface 106 which allows thedriver arm to be coupled to an aerodynamic high lift device, such asflap or a spoiler.

The actuator 50 can cause the gimbal 60 to translate. For example, theactuator can generate a rotational output, which causes the shaft 58 torotate. In one embodiment, the shaft 58 can be up to twenty inches long.However, longer shafts can be utilized and this example is provided forthe purposes of illustration only. The rotation of the shaft 58 cancause the gimbal 60 to translate along path 59 in either directiondepending on the rotational direction of the shaft.

The translational movement of the gimbal 60 can cause the first end ofthe driver arm 102 to translate and rotate about a rotational axis 54 atthe rotational interface 104. The translational motion at the rotationalinterface 104 can cause a movement at the second end of the driver armat interface 106. The movement at the interface 106 can generateadditional movements, which can be transferred directly or via one ormore mechanical linkages to the aerodynamic high lift device which cancause the aerodynamic high lift device to actuate. For example, a flapcan rotate upwards or downwards in response to the translational motionof the gimbal 60

FIG. 7 is block diagram of a method 200 of assembling a gimbal, such asthe gimbal described above with respect to FIGS. 2-6B. In 202, a nut canbe interfaced with a shaft. For example, the nut and the shaft can bethreaded and the nut can be threaded onto the shaft.

In 204, the first receiver and the second receiver can be placed aroundthe nut. In one embodiment, the nut can have a first post and a secondpost and the first receiver and the second receiver can have openingswhich receive the first post and the second post. The nut can bedisposed in a second aperture formed by the first receiver and thesecond receiver such that it is surrounded by the first receiver and thesecond receiver. In one embodiment, the first receiver and the secondreceiver can have a common and identical shape.

In 206, the first receiver can be secured to the second receiver usingat least one fastener. For example, a plurality of pins or bolts can beused to secure the first receiver to the second receiver. When secured,the first receiver and the second receiver can be designed to haveportions which contact one another when placed around the nut.

The first receiver and the second receiver can include a firstrotational attachment point and a second rotational attachment point,respectively. In 208, a rotational interface can be provided whichutilizes the first rotational attachment point and the second rotationalpoint. The rotational interface can be used to secure a driver arm tothe gimbal. When the gimbal translates, the driver arm can translate androtate about a rotational axis associated with the rotational interface.As described above, during operation, this connection scheme can helpprevent the shaft from being bent.

Examples of Aircraft Application

An aircraft manufacturing and service method 400 shown in FIG. 8 and anaircraft 500 shown in FIG. 9 are now described to better illustratevarious features of processes and systems presented herein. Duringpre-production, aircraft manufacturing and service method 400 mayinclude specification and design 404 of aircraft 500 and materialprocurement 406. The production phase involves component and subassemblymanufacturing 408 and system integration 410 of aircraft 500. Forexample, the gimbals described above with respect to FIGS. 2-7 can beassembled and installed in this step. System integration can also occurbefore material procurement 406. Thereafter, aircraft 500 may go throughcertification and delivery 412 in order to be placed in service 414.While in service by a customer, aircraft 500 is scheduled for routinemaintenance and service 416 (which may also include modification,reconfiguration, refurbishment, and so on). While the embodimentsdescribed herein relate generally to servicing of commercial aircraft,they may be practiced at other stages of the aircraft manufacturing andservice method 400.

Each of the processes of aircraft manufacturing and service method 400may be performed or carried out by a system integrator, a third party,and/or an operator (e.g., a customer). For the purposes of thisdescription, a system integrator may include, without limitation, anynumber of aircraft manufacturers and major-system subcontractors; athird party may include, for example, without limitation, any number ofvendors, subcontractors, and suppliers; and an operator may be anairline, leasing company, military entity, service organization, and soon.

As shown in FIG. 9, aircraft 500 produced by illustrative aircraftmanufacturing and service method 400 in FIG. 8 may include airframe 518with a plurality of high-level systems 520 and interior 522. Examples ofhigh-level systems 520 include one or more of propulsion system 524,electrical system 526, hydraulic system 528, and environmental system530. Any number of other systems may be included. For example, theassemblies including a split gimbal, such as shown in FIGS. 2-7 can beutilized. Apparatus and methods shown or described herein may beemployed during any one or more of the stages of the aircraftmanufacturing and service method 400. For example, components orsubassemblies corresponding to component and subassembly manufacturing408 may be fabricated or manufactured in a manner similar to componentsor subassemblies produced while aircraft 500 is in service. Also, one ormore aspects of the apparatus, method, or combination thereof may beutilized during steps 408 and 410, for example, by substantiallyexpediting assembly of or reducing the cost of aircraft 500. Similarly,one or more aspects of the apparatus or method realizations, or acombination thereof, may be utilized, for example and withoutlimitation, while aircraft 500 is in service, e.g., maintenance andservice 416.

Conclusion

Different examples and aspects of the apparatus and methods aredisclosed herein that include a variety of components, features, andfunctionality. In particular, apparatus and methods associated with agimbal are described. The gimbal can be used with an assembly that isused to actuate a high lift device on a wing used on an aircraft. Itshould be understood that the various examples and aspects of theapparatus and methods disclosed herein may include any of thecomponents, features, and functionality of any of the other examples andaspects of the apparatus and methods disclosed herein in anycombination, and all of such possibilities are intended to be within thespirit and scope of the present disclosure. Many modifications and otherexamples of the disclosure set forth herein will come to mind to oneskilled in the art to which the disclosure pertains having the benefitof the teachings presented in the foregoing descriptions and theassociated drawings.

What is claimed is:
 1. A gimbal comprising: a nut having a first post, asecond post and a first aperture wherein the first aperture isconfigured to receive a shaft; a first receiver including i) a first topportion, which partially surrounds the first post, ii) a first bottomportion, which partially surrounds the second post and iii) a firstrotational attachment point; a second receiver including i) a second topportion, which partially surround the first post, ii) a second bottomportion, which partially surround the second post and iii) a secondrotational attachment point; at least one fastener which secures thefirst receiver to the second receiver to form a second aperture whereinthe nut is disposed within the second aperture; wherein the gimbal isconfigured to receive a force via the shaft which causes the gimbal totranslate wherein a translational movement of the gimbal causes a driverarm coupled to the first rotational attachment point and the secondrotational attachment point to rotate about a rotational axis.
 2. Thegimbal of claim 1, wherein the nut is threaded and is configured toreceive a threaded shaft and wherein the threaded shaft is configured torotate which causes the gimbal to translate along the threaded shaft. 3.The gimbal of claim 1, wherein the nut is secured at a fixed location tothe shaft and wherein the translational movement of the shaft causes thegimbal to translate.
 4. The gimbal of claim 1, wherein the firstreceiver and the second receiver have a common shape.
 5. The gimbal ofclaim 1, wherein the second aperture is circular and wherein a diameterof the second aperture is smaller than a height of the nut between thefirst post and the second post.
 6. The gimbal of claim 1, furthercomprising a first bushing which covers the first post and a secondbushing which covers the second post wherein the first top portion andthe second top portion surround the first bushing and the first post andwherein the first bottom portion and the second bottom portion surroundthe second bushing and the second post.
 7. The gimbal of claim 6,further comprising a first fastener coupled to the first receiver andthe second receiver configured to secure the first bushing in place anda second fastener coupled to the first receiver and the second receiverconfigured to secure the second bushing in place.
 8. The gimbal of claim1, wherein the driver arm is coupled to an aerodynamic high lift device.9. The gimbal of claim 1, wherein the driver arm is coupled to thegimbal via the first rotational attachment point and the secondattachment point to prevent the shaft from being bent when the gimbaltranslates.
 10. An assembly for actuating an aerodynamic high liftdevice on an aircraft comprising: an actuator coupled to a shaft whereinthe shaft is configured to receive a force from the actuator; a gimbalincluding; a nut having a first post, a second post and a first aperturewherein the aperture is configured to receive the shaft; a firstreceiver including i) a first top portion, which partially surrounds thefirst post, ii) a first bottom portion, which partially surrounds thesecond post and iii) a first rotational attachment point; a secondreceiver including i) a second top portion, which partially surround thefirst post, ii) a second bottom portion, which partially surround thesecond post and iii) a second rotational attachment point; at least onefastener which secures the first receiver to the second receiver to forma second aperture wherein the nut is disposed within the secondaperture; a driver arm rotationally coupled to the first rotationalattachment point and the second rotational point on a first end and theaerodynamic high lift device on a second end; and the aerodynamic highlift device; wherein the force from the actuator causes the gimbal totranslate, which causes the first end of the driver arm to translate androtate about a rotational axis, which transfers a second force to thesecond end of the driver arm, wherein the second force causes theaerodynamic high lift device to actuate.
 11. The assembly of claim 10,wherein the assembly is located in one of a wing of an aircraft, ahorizontal stabilizer of the aircraft or a vertical stabilizer of theaircraft.
 12. The assembly of claim 10, wherein the driver arm iscoupled to the gimbal via the first rotational attachment point and thesecond attachment point to prevent the shaft from being bent when thegimbal translates.
 13. The assembly of claim 10, wherein the nut isthreaded and is configured to receive a threaded shaft and wherein theshaft is configured to rotate which causes the gimbal to translate alongthe shaft.
 14. The assembly of claim 13, further comprising an end capattached at the end of the shaft which is configured to keep the nutfrom rotating off of the shaft.
 15. The assembly of claim 10, whereinthe nut is secured at a fixed location to the shaft and wherein atranslational motion of the shaft causes the gimbal to translate. 16.The assembly of claim 10, wherein the first receiver and the secondreceiver have a common shape.
 17. The assembly of claim 10, wherein thesecond aperture is circular and wherein a diameter of the secondaperture is smaller than a height of the nut between the first post andthe second post.
 18. The assembly of claim 10, further comprising afirst bushing which covers the first post and a second bushing whichcovers the second post wherein the first top portion and the second topportion surround the first bushing and the first post and wherein thefirst bottom portion and the second bottom portion surround the secondbushing and the second post.
 19. A method of assembly comprising:attaching a shaft to an actuator; attaching a nut including a first postand a second post to the shaft; attaching a first receiver and a secondreceiver to the first post and the second post of the nut wherein thefirst receiver and the second receiver surround the nut and fix anorientation of the nut relative to the first receiver and the secondreceiver and wherein the first receiver includes a first rotationalattachment point and wherein the second receiver includes a secondrotational attachment point; attaching the first receiver to the secondreceiver; and attaching a driver arm on a first end to the firstrotational attachment point and the second rotational attachment pointwherein the driver arm is rotationally coupled to the first rotationalattachment point and the second rotational attachment point.
 20. Themethod of claim 19, wherein the actuator is configured to apply a forceto the shaft which causes the nut, the first receiver and the secondreceiver to translate, which causes the first end of the driver arm totranslate and to rotate about a rotational axis through the firstrotational attachment point and the second rotational attachment point,which transfers a second force to the second end of the driver arm,which causes an aerodynamic high lift device to actuate.
 21. The methodof claim 20, wherein the force is rotational force which causes theshaft to rotate, which causes the nut, the first receiver and the secondreceiver to translate along the shaft.
 22. The method of claim 20,wherein the nut and the shaft are threaded.